UA142098U - INCLINED RANGE MEASUREMENT CHANNEL TO AIRCRAFT WITH ADVANCED POSSIBILITIES FOR MOBILE SINGLE POINT MEASURING SYSTEM - Google Patents

Abstract

The channel for measuring the inclined range to aircraft with advanced capabilities for a mobile single-point measuring system includes a control element, a deflector control unit, a pump with a laser, a modified longitudinal mode selector, prisms for the frequency of intermode bits Δνm, a block of deflectors , transmitting optics, optoelectronic module, which consists of television and infrared channels, receiving optics, photodetectors, broadband amplifier, resonant amplifiers tuned to the appropriate frequencies of intermode bits, pulse shaper, circuit "i", differential filtering with setpoint chain, rectifier, flip-flop, detector, differentiated optics, amplifier, filter, meter and electronic computer, advanced unit with input b, satellite radio navigation systems equipment, gyro-stabilized platform and b - signal input from the measuring channel and aircraft. Additionally, a radar module was introduced.

Description

The proposed useful model belongs to the field of telecommunications and can be used to build a mobile single-point measuring system (MSMS).

The well-known "Slant range measurement channel to aircraft with enhanced capabilities for a mobile combined measurement system" (1|, which contains a control element (KE), a deflector control unit (BKD), a pumped laser (Li), a modified longitudinal mode selector (MSPM ), prisms for DAm intermode beat frequency, deflector block (BD), switch for Amma and 2 Amma intermode beat frequencies, transmission optics (PRDO), optical-electronic module (OEM), which consists of television and infrared channels, receiving optics ( PRMO), photodetectors (FTD), broadband amplifier (SP), resonance amplifiers (RP), tuned to the corresponding frequencies of intermode beats, pulse shaper (PI), trigger ("1"07, circuit "and" ("7"), counter (Lch), filter with a given bandwidth (Fp), detector (D), differential optics (DO), amplifier (P), filter (F), differential circuits (DL), rectifiers (Vyp), electronic computing machine ( EOM), block with extended capabilities (BRM) with vv b, gyro-stabilized platform (GSP) and b - signal input from the channel for measuring the angular velocities of the aircraft (LA).

The disadvantage of the well-known channel is that it does not provide operational high-precision navigation.

The closest analog to the proposed useful model is "An aircraft slant range measurement channel with enhanced capabilities for a mobile combined measurement system" (2)|, which contains a control element, a deflector control unit, a pumped laser, a modified longitudinal mode selector, prisms for frequencies of intermode beats Dum, block of deflectors, switch for frequencies of intermode beats Dum and 2Dum, transmission optics, optical-electronic module, which consists of television (and infrared) channels, receiving optics, photodetectors, broadband amplifier, resonant amplifiers tuned to the appropriate frequencies of intermode bits, pulse shaper, "yi" circuit, bandpass filter, differential circuit, rectifier, flip-flop, detector, differential optics, amplifier, filter, counter, electronic calculator, b-input advanced unit, satellite radio navigation system equipment (ASRNES), gyrostable ized platform and b - signal input from the channel for measuring the angular velocities of the aircraft.

The disadvantage of the channel - the closest analogue - is that it cannot conduct external trajectory measurements and search for aircraft in adverse conditions.

The useful model is based on the task of creating a channel for measuring the inclined distance to aircraft with enhanced capabilities for a mobile single-point measuring system, which will allow high-precision measurement of the inclined distance to an aircraft in a wide range of distances, starting from the initial moment of its flight, and detailed recognition of the aircraft in a short time , objective control at night and day, processing, display and storage of information obtained during the testing of the aircraft, compliance with the spatial stabilization of the platform, on which the combined receiving and transmitting equipment and executive mechanisms (VM) are placed at the corners of the VD, operational high-precision navigation and, if necessary, search for aircraft at any point of the range, at any time of the year and day, in any weather.

The task is solved due to the fact that the channel has the closest analogue, which contains a control element, a deflector control unit, a pumped laser, a modified selector of longitudinal modes, prisms for the frequency of intermode beats Doom, a block of deflectors, a switch for the frequencies of intermode beats Doom and 2Aum , transmitting optics, an optical-electronic module, which is composed of television and infrared channels, receiving optics, photodetectors, a broadband amplifier, resonant amplifiers tuned to the appropriate frequencies of intermode bits, a pulse shaper, an "and" circuit, a filter with a given bandwidth, a differential chain . model, additionally introduced ra location module (RM).

The construction of the oblique range measurement channel to the aircraft with enhanced capabilities for a mobile single-point measurement system is associated with the use of a single-mode multi-frequency with synchronization of the longitudinal modes of radiation of a single laser-transmitter, the time-frequency method (FM) of measurement (ZI, OEM and RLM.

The technical result that can be obtained when implementing a useful model consists in high-precision measurement of the inclined range to the aircraft, its detailed recognition in a very short time, the implementation of objective control in day and night conditions, operational processing,

displaying and saving the received information, high-precision navigation and, if necessary, searching for aircraft at any point of the range, at any time of the year and day, in any weather.

In Fig. 1 shows the transmission side of the generalized structural diagram of the proposed channel, where: b - signal input from the channel for measuring angular velocities of aircraft; | - measuring signal; AI - a signal with spatial modulation of polarization, AI - a combined signal in the visible and infrared ranges.

In Fig. 2 shows the creation of equal-signal direction (RSD) and scanning with 4 directional diagrams (DS) of laser radiation (LV) in orthogonal planes.

In Fig. C shows the creation of a laser signal with spatial polarization modulation.

In Fig. 4 shows a generalized structural diagram of the proposed channel.

In Fig. 5 shows voltage diagrams from the outputs of the units for measuring the inclined distance to the LA, where: a) from the reference signal unit; b) from the block of the reflected signal.

The proposed inclined range measurement channel to aircraft with advanced capabilities for a mobile single-point measurement system includes a control element 1, a deflector control unit 2, a pumped laser 3, a modified longitudinal mode selector 4, prisms for the intermode beat frequency Doom, a deflector unit 5, a switch for frequencies of intermode bits Dum and 2Dum, transmitting optics b, optical-electronic module 7, which is composed of television and infrared channels, receiving optics 8, photodetectors 9, broadband amplifier 10, resonant amplifiers 11, tuned to the corresponding frequencies of intermode bits, pulse shaper 12 , AND circuit 13, band-pass filter 14, differential circuit 15, rectifier 16, flip-flop 17, detector 18, differential optics 19, amplifier 20, filter 21, counter 22 and electronic calculator 23, advanced unit 24 with the introduction of b, equipment of satellite radio navigation systems 25, radar ionic module 26, gyro-stabilized platform 27 and b - signal input from the channel for measuring the angular velocities of the aircraft.

The operation of the proposed inclined range measurement channel to aircraft with enhanced capabilities for a mobile single-point measurement system is as follows.

From the synchronized single-mode multi-frequency radiation spectrum of the laser-transmitter (Ln) with the help of MSPM, the necessary pairs of frequencies and individual frequencies are isolated to create: a laser signal with spatial modulation of polarization, provided the signal from longitudinal modes (carrier frequencies) is used;

RSN based on the formation of the total DS LV, due to the 4th partial DS LV, partially intersecting, provided that combinations of longitudinal modes are used ("tinted" by the difference frequencies of intermode beats)

Duva-uv5-u4 "Dum, Du97-mu9-u7-eDum,

Duvz-uv-uz-ZADum, Duv2-uv-u2-6bDum

With the help of MSPM and BRM, a laser signal with spatial modulation of polarization is formed by creating a LV from two carrier frequencies (mi and mpg) in the form of two beams with vertical ((mpi) and horizontal (ugg) polarization (Fig. 3). At the same time, the radiation of the aperture of the first and second polarization channels in the aperture plane of MYO are spaced at a known distance Dum.

The difference in the path of the beams to the LA HOU picture plane varies along the X axis from point to point. Due to this, the difference in phases (amplitudes) between the polarized components, which are orthogonal, of the field in the picture plane also changes from point to point.

Depending on the difference in phases (amplitudes) in the picture plane, the form of polarization of the total field of the probing signal changes from linear through elliptical and circulating to linear, orthogonal to initial, etc. The period of change in the form of polarization is determined by the base between the emitters of the duad and the distance to the picture plane B.

The intensity distribution in the registered image of the aircraft is modulated according to the harmonic law with a modulation factor equal to the value of the degree of polarization of the radiation reflected in this area of the aircraft surface.

The signal of the frequencies of intermode beats Dum, 2Dum, ZDum and bDum enters the DB consisting of 4 piezoelectric deflectors. Partial DS LV scan the DB in pairs in each of two orthogonal planes (Fig. 1, 2). The scanning period is set by the BKD, which, together with the LN, is powered by the KE.

Passing through the PRDO, the group laser pulse signal of frequency pairs у, у4-Dum, hvo, 60 ut-2Dum, uv, Uuz-ZDum and uv, m2-6Dum is focused into the scanned points of space, since counter-scanning is carried out by two pairs of DS LV in each from two orthogonal planes si B (or X and Y). At the same time, a laser signal with spatial modulation of polarization (at carrier frequencies (mi and upg) passes along the RON (Fig. 2).

Laser pulse signals received by PRMO from LA and envelope signals of DS LV, reflected in the process of scanning four DS LV, are converted into electrical pulse signals at the carrier frequency and difference frequencies of intermode bits with the help of FTD.

Amplified SP, they are distributed: in the BRM for processing the laser signal reflected from the surface of the aircraft with spatial modulation of the probing polarization; according to RP, which are tuned to the corresponding frequencies of intermode beats Dum from, 2Aum from, ZDuUm from, bLDuUm from.

When a laser signal with spatial modulation of the probing polarization is reflected from the LA surface, the amplitude and phase relationships between the orthogonally polarized components, their polarization parameters and, accordingly, the complex coherence coefficients of the reflected field change.

The spatial distribution of the polarization characteristics of such a reflected signal according to the change in the contrast of the modulation structure of the image also carries information about the types of materials in the composition of the surface of the aircraft, their characteristics, etc., which is displayed in the computer. Therefore, the BRM performs polarization processing of the received field.

At the same time, pulsed radio frequency signals coming from RP 1 (RP Dum from) form a signal about the slant range to the LA, and RP 4 (RP bdum from), RP 2 (RP 2Aum from and RP Z (RP ZdDum from) - signals for other measuring channels of the Ministry of Internal Affairs and Communications.

The principle of operation of the coarse scale of the channel for measuring the inclined distance to the aircraft (in the structure

MIA) consists of the following (Fig. 4, 5).

On the transmitting side.

The MSPM selected from the LV spectrum is the first pair of uh frequencies. is split under the action of a splitter (prisms) into two optical signals: 1) the main - scanned DB at a certain angle (with time Tpr, set by the BKD), which passes through a switch to select a "bSlanking" pulse (blank - zero) and a splitter, where the additional signal (2) is allocated, and is sent to the PRDO and then to the LA;

From 2) additional (1) - converted FTD into an electric pulse signal of the difference frequency of the intermode beat Dum, arrives at Fi, where the "bundles" of pulses received by the circuit "I" are allocated.

The additional optical signal of the UZ frequency received from the FTD with "bSlanking" pulses, converted into a Dum signal, acquires clear boundaries of the "bSlanking" pulse and, passing through TO, is amplified.

A filter with a bandwidth of P-1/1 (where those are the duration of the pulse) separates "blank" pulses from the general signal - signals that, passing through the DL and Vyp (FI-DLeVyp), are separated in the form of one short pulse for the beginning of the "blank" pulse and arrive at Tr with the index "1", including it.

On the receiving side.

Reflected from the LA, the main signal of UZ frequencies in the sum of the group signal, bypassing the PRMO, is transformed by the FTD into an electrical pulse signal Dum, amplified by the SP and allocated in

RP, as a signal of the intermode frequency Dum from and, Passing through Det, is transformed in exactly the same way as the additional electrical signal (2) of the frequency Dum, arrives only at Tr with the index "0", "overturning" it. The signal coming from TR to circuit "I" periodically "opens" and "closes" the passage for "bundles" of pulses from FI, which are counted by Lch and processed by EOM in the form of a number that corresponds to the value of the slope distance to LA.

In this way, the oblique range to the LA is measured on a rough scale. The transition to the exact scale (generation of picosecond pulses) is carried out immediately after the switch is turned on (to form a "blank" pulse).

Since the channel for measuring the inclined range to the LA is proposed to be included in the structure

MOVS, then switching on and off the switch occurs simultaneously for 2 pairs of frequencies ul and

IN.

Hardware errors of measuring the inclined distance to the aircraft in the proposed channel are errors in determining the beginning and end of the time interval, errors due to the discreteness and instability of the clock (counting) pulse frequency.

The accuracy of the interval estimation is determined by the steepness of the envelope at a given limit value of the voltage n and depends on the shape of the scanning DS LV and the signal/noise ratio.

The optical-electronic module constantly monitors the aircraft being accompanied in day and night conditions in the visible and infrared ranges. Information about objective control and oblique range to the aircraft is displayed on the computer monitor.

To save the information processed during LA tests in memory

A computer uses a database - a set of interrelated data organized according to a data scheme in such a way that the user can work with them.

Increasing the speed of processing information received by a computer is carried out due to the parallelization of the process of building one decision tree and their ensembles.

Measurement information about the angular velocities of the aircraft is used in the BRM, where due to the additional processing of the elements of the polarization matrix of the aircraft scattering from the obtained polarization field, the exact value of the angular velocities of the aircraft is ensured, the set of signs of its recognition is expanded, and the efficiency of the recognition of the accompanying aircraft is increased.

The equipment of satellite radio navigation systems provides an opportunity at any point on the earth's surface, at any time of the year and day, in any weather to determine (specify) the parameters of the MIA - three coordinates and three components of the velocity vector.

Depending on the weather conditions (rain, snow, etc.), the capture of the RLM to accompany the aircraft begins by viewing the area of space where the aircraft is located. The support of the RLM continues until it switches to the automatic support of the OEM (total DS).

Information from the RLM is sent to the computer.

The gyro-stabilized platform ensures compliance with the spatial stabilization of the channel platform, on which the combined receiving-transmitting equipment and VM are placed at the angles of azimuth a and location of the VD.

The formation of DS LV and the creation of RSN is connected with the satisfaction of strict requirements for the radiation spectrum of a single-mode multifrequency laser-transmitter, i.e., high-precision synchronization of longitudinal modes and stabilization of the frequencies of intermode beats.

Sources of information: 1. Utility model patent Mo 107050, Ukraine, IPC 2015 17/42, 2015 17/66. Channel

From the measurement of inclined distance to aircraft with enhanced capabilities for a mobile combined measuring system /1.V. Shchypanskyi, P.V. Openko, O.V. Kolomiytsev and others. - MO and 201508052; statement 12.08.2015; published 05/25/2016; Bul. Mo. 10. - 11 p.m. 2. Utility model patent No. 132115, Ukraine, IPC 2015 17/42, 2015 17/66. The inclined range measurement channel for aircraft with enhanced capabilities for a mobile single-point combined measuring system /V.V. Tyurin, A.G. Saliy, P.V. Openko et al. - MO and 201809315; statement 12.09.2018; published 11.02.2019; Bul. Mo. 3. - 9 p. 3. Utility model patent Mo 55645, Ukraine, IPC 2015 17/42, 2015 17/66. Time-frequency method of search, recognition and measurement of aircraft motion parameters /0.V.

Kolomiytsev - MO i201005225; statement 29.04.2010; published 27.12.2010; Bul. Mo. 24. - 14 p.m.

Claims (1)

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